JP2015522467A - System for removably connecting unmanned aircraft in a launch tube - Google Patents

Abstract

A launch tube (100) of an unmanned aerial vehicle (UAV) comprising at least one layer of a prepreg substrate provided around an opening (106) to form a tube, and disposed within the tube (100); A firing tube (110) having a first stopper tab (126) and a stopper (124) removably connected to the first stopper tab and in contact with the inner peripheral wall (102) of the tube (100). The stopper (124) is rotationally restrained by the inner peripheral wall (102) and the first stopper tab (126). [Selection] Figure 1

Description

CROSS REFERENCE TO RELATED APPLICATIONS This application claims priority and benefit of provisional patent application No. 61 / 656,949, filed on June 7, 2012, the contents of which are hereby incorporated by reference for all purposes. Incorporated in the description.

  The present invention relates to a launch tube having a launch tube, and more specifically to a launch tube and canister for an unmanned aerial vehicle (UAV), a silent launch tube, and a launch tube.

  Usually, the UAV is transported to the launch site in an unassembled state. At the launch site, they are assembled, inspected, and fired. Firing is typically performed manually, by an elastic tether, by an electric winch, from a moving vehicle, or some combination thereof. Such methods are time consuming and / or cumbersome. Once fired, the UAV may be transmitted, for example, via supervisory control, by a person in the loop, intermittently uplinking a trajectory correction, or by an onboard flight path guidance generator and / or an inertial sensor and / or It may be derived by receiving an uplink from an intercept / attack site preloaded in combination with the output of a Global Positioning System (GPS) receiver.

  An unmanned aerial vehicle (UAV) launch tube apparatus is disclosed that includes at least one layer of a prepreg substrate provided around an opening to form a tube and a first stop tab disposed within the tube. And a stopper that is detachably connected to the first stopper tab and is in contact with the inner peripheral wall of the tube, the stopper being rotationally restrained by the inner peripheral wall and the first stopper tab. Has been. The launcher may also include an expandable skirt that provides a pressure seal with the inner wall of the tube. The expansion skirt may be axially constrained in the tube using an adhesive, and the adhesive may removably couple the expandable skirt around a shell in the tube. In such embodiments, the shell may include an outer surface of a gas generator, the gas generator generating gas to create a high pressure volume between the expandable skirt and the shell. Configured and this generated pressure is sufficient to push the expandable skirt away from the shell by breaking the adhesive restraint between the outer surface of the gas generator and the expandable skirt. is there. The apparatus may also include a UAV installed on the launch tube, the UAV having a second stop tab removably coupled to the stop, the stop being The inner peripheral wall, the first stopper tab, and the second stopper tab are rotationally restricted. The launch tube may be anchored to the tube. The launcher is configured to engage the UAV and has a first plurality of partially expandable skirt seals, a base launcher installed on the base launcher, and a second plurality of partial extensions. A circumferential firing skirt having a movable skirt seal, wherein the first and second plurality of partially expandable skirt seals complete the inner wall pressure seal. The expandable skirt may be axially constrained within the tube using an adhesive, the adhesive may removably couple the expandable skirt around a shell in the tube, and the gas Generation of gas by the generator pushes the expandable skirt away from the gas generator by breaking the removable bond of the adhesive. The UAV may be installed on the launch tube, the UAV has a second stopper tab detachably connected to the stopper, and the inner peripheral wall is disposed while the UAV is in the tube. In addition, the stopper is prevented from coming off from the second stopper tab.

  A method for launching an unmanned aerial vehicle (UAV) is disclosed that includes generating a gas in a gas generator, and the high pressure volume between the expandable launcher skirt of the launcher and the gas generator. Breaking the adhesive bond that restrains the launcher within the launch tube, and using the gas to push the expandable launcher skirt against the inner peripheral wall of the launcher; and Pushing up the launch tube above the launch tube with gas. The method may also be defined such that the adhesive bond includes an adhesive bond between the expandable skirt and a shell around the gas generator. The method also includes securing a UAV to the launch tube using a stop, and restraining the stop against an inner peripheral wall of the launch tube, the stop being one of the UAV and the launch tube. There may be a step of preventing separation from at least one. In some embodiments, the method also includes the step of sliding the stop through the inner peripheral wall to release at least one of the UAV and the launcher from the stop. The firing tube may be anchored to the firing tube to prevent the firing tube from exiting the firing tube.

  In another embodiment, a method for launching an unmanned aerial vehicle (UAV) includes constraining a launch tube in a launch tube and introducing gas into the high pressure side of the expandable launcher skirt of the launch tube to introduce the launch tube in the launch tube. Breaking the restraint; pushing the expandable launcher skirt against the inner peripheral wall of the launch tube using the gas; and pushing the launcher up the launch tube using the gas; , With. In such embodiments, the launch tube may be constrained with an adhesive, the adhesive being used to constrain the expandable skirt of the launch tube to a shell around the gas generator in the launch tube. May be used. The method may also include mooring the launch tube to the launch tube. The expandable launcher skirt may also include a circumferential skirt projection that extends from the expandable launcher skirt toward the inner peripheral wall of the launch tube. The method may also include the step of restricting movement of the launcher by a tether configured to prevent the launcher from exiting the launcher, wherein the restriction of movement of the launcher includes: A gas is substantially retained within the firing tube. In some embodiments, the tether may be attached to the firing tube and the inner peripheral wall of the firing tube by a tether reel and / or winding device.

  In another embodiment, an unmanned aerial vehicle (UAV) launch tube device includes: a first opening having a constant cross-sectional area; and an enlarged cross-sectional area compared to the first opening. A second opening, wherein the first opening and the second opening form a launch tube; and are arranged in the first opening and configured to be detachably connected to the UAV. The launcher is configured to be detached from the UAV when the launcher moves from the first opening to the second opening. The launcher may be configured to be detachably coupled to the UAV by a stop, the stop being connected to a first stop tab of the launcher and a second stop tab of the UAV. It is configured to be detachably connected. The stop may be rotationally constrained by at least one of: an inner surface of the first opening, a first stop tab of the launch tube, and a second stop tab of the UAV. The stop may be configured to detach from the second stop tab of the UAV when the launcher moves from the first opening to the second opening. The stopper may be configured to detach from the first stopper tab of the firing tube when the stopper moves through the inner surface of the second opening. In some embodiments, also, at least one gas generator disposed at the bottom of the first opening; and an expandable launcher skirt of the launcher, the open end of the expandable launcher skirt And an expandable launcher skirt that is directed to the at least one gas generator and is axially constrained by a detachable restraint. The at least one gas generator may be configured to generate gas and the expandable launcher skirt may be configured to substantially retain the gas in the launch tube. The generated gas may be configured to disengage the expandable launcher skirt from the removable restraint and propel the launcher from the first opening to the second opening. The expandable launcher skirt may be configured to expand to an enlarged cross-sectional area of the second opening to keep the gas substantially retained within the second opening of the launch tube. Some embodiments may further comprise a tether attached to the bottom of the launcher and the first opening, the tether configured to limit movement of the launcher and being expandable. The launcher skirt substantially retains the gas from leaking through an opening in the launch tube.

  The embodiments are illustrated by way of example and are not limited to the figures of the accompanying drawings.

FIG. 1 shows one embodiment of an expandable skirt coupled to a shell in a launch tube using an adhesive and a launch tube removably coupled to a UAV. FIG. 2 is an enlarged view of the expandable skirt, adhesive, and shell shown in FIG. 1, with gas pressure being formed at a high pressure volume relative to the expandable skirt. FIG. 3 is an enlarged view of the expansion skirt, adhesive, and shell initially shown in FIG. 1 with the expandable skirt fractured of the adhesive bond restraining the firing tube within the firing tube. FIG. 4 shows how the gas pushes up the launch tube above the launch tube shown in FIG. 1, and the launch tube is detachably connected to the UAV using a stop, and the stop is connected to the launch tube. Restrained by the inner wall. FIG. 5 shows an exemplary UAV launch tube and, in one embodiment, a launch tube removably coupled to the UAV using a stop, the stop being constrained by the inner wall of the launch tube. FIG. 6 shows an exemplary UAV launch tube and, in one embodiment, a launch tube removably coupled to the UAV using a stop, the stop being constrained by the inner wall of the launch tube. FIG. 7 shows a view of the stop shown in FIGS. 5 and 6 coming off the UAV with the inner wall restraint removed. FIG. 8 shows an exemplary UAV launch and, in one embodiment, a launcher releasably coupled to the UAV using a stop, the stop of the launch tube within a portion of the launch tube. Restrained by the inner wall. FIG. 9 illustrates an exemplary UAV launch and, in one embodiment, a launcher removably coupled to the UAV using a stop, the stop being a launch tube within a portion of the launch tube. Restrained by the inner wall. FIG. 10 shows the stop shown in FIGS. 8 and 9 with the inner wall restraint removed in other parts of the launch tube and coming off the UAV. FIG. 11 shows a UAV launch tube having an enlarged open launch end and a UAV and launch tube coupled to a stop in another embodiment, the stop being launched within a portion of the launch tube. Restrained by the inner wall of the tube. FIG. 12 shows a UAV launch tube having an enlarged open launch end and a UAV and launch tube coupled to the stop in another embodiment, where the stop is within a portion of the launch tube. Restrained by the inner wall of the tube. FIG. 13 shows an exemplary UAV with the wings deployed and its propellers rotating. FIG. 14 shows an exemplary UAV with the wings deployed and its propeller props rotating.

  An unmanned aerial vehicle (UAV) launch tube apparatus is disclosed that includes a prepreg substrate provided around an opening to form a tube, a launch tube disposed within the tube and having a first stop tab; A stopper that is detachably connected to the first stopper tab and contacts the inner peripheral wall of the tube, the inner peripheral wall being disengaged from the first stopper tab while the UAV is in the tube. Suppresses This approach allows the UAV to be assembled, inspected and constrained within the launch tube before being moved further to the launch site.

  FIG. 1 illustrates one example of a UAV 108 that is removably restrained within a launch tube 100 for further inspection and / or further movement to a launch site. The launch tube 100 has an inner peripheral wall and an outer peripheral wall (102, 104) provided around the opening 106. In some embodiments, the launch tube 100 is formed with a single layer structure. The UAV 108 is shown in close proximity to the inner peripheral wall 102 in the opening 106, and the UAV 108 is detachably coupled to a launch tube 110 that is itself disposed in the launch tube 100. The launch tube 110 is hollow and has an open end 112 directed to the high pressure volume 114 side. A tether 116 is attached to the launch tube 110 in the hollow interior of the launch tube 110 and is also attached to the inner wall 102 of the launch tube 100.

  The UAV 108 has a radial recess 118 at the proximal end 120 of the UAV 108 from which a UAV stop tab 122 extends radially toward the inner peripheral wall 102 for coupling to the stop 124. Similarly, the launch tube 110 has a stop tab 126 that extends radially toward the inner peripheral wall 102 to connect to the stop 124 from a radial recess 128 at the proximal end 130 of the launch tube 110. As shown in FIG. 1, these UAV stop tabs and launcher stop tabs (122, 126) are complementary and rotationally aligned opposite each other so that a stop 124, eg, U-shaped, Both the UAV and launcher stop tabs (122, 126) can be removably enclosed. For example, each of the UAV and launcher stop tabs (122, 126) may form a horizontal and flat surface, or a substantially horizontal and substantially flat surface, with the stop 124 being a UAV and launcher stop tab ( 122, 126), the complementary portions of the stop 124 sit on these faces. When the UAV 108, the launch tube 110, and the stop 124 are inserted into the launch tube 100, the inner peripheral wall 102 is such that both the UAV stop tab 122 and the launcher stop tab 126 are not separated. The stop 124 is rotationally constrained to achieve the coupling of the UAV 108 and the launch tube 110, which can be removed when the inner wall 102 no longer rotationally constrains the stop 124.

  In an alternative embodiment, the stop 124 is detachably connected to the UAV stop tab 122 with a hinge (not shown) and is rotatably connected to the launch tube 110. In such an embodiment, for example, when the UAV 108 and stop 124 begin to exit the launch tube 100 or the diameter of the opening 106 increases appropriately, the rotational restraint of the stop 124 by the inner peripheral wall 102 is removed. The stop 124 is rotatable around a hinge (not shown).

  The launch tube 110 is formed or assembled with an expandable skirt 132, which is axially constrained and removably coupled to the inner wall 102 of the launch tube 100 downstream of the gas generator 134. Yes. As shown in FIG. 1, the expandable skirt 132 is removably coupled to the circumferential shell 136 within the tube using an adhesive bond 138 so that a high pressure volume 114 is provided between the expandable skirt 132 and the circumferential shell 136. Established. The circumferential shell 136 is defined by the outer surface of the gas generator 134. In operation, gas from the gas generator 134 is introduced into the high pressure volume 114. The resulting gas pressure pushes and expands the expandable skirt 132 at the adhesive bond 138 and releases the expandable skirt 132 from the circumferential shell 136. The pressure generated at the expandable skirt 132 results in or at least facilitates the formation of a gas seal between the launch tube 110 and the inner peripheral wall 102 of the launch tube 100, and the high pressure volume 114 and the opposite side of the high pressure volume of the launch tube The launch tube 110 is better driven along the inner wall 102 of the launch tube 100 using the difference in gas pressure between The formation of a pressure seal between the expandable skirt 132 and the inner peripheral wall 102 is facilitated by a circumferential skirt protrusion 140 formed in the expandable skirt 132 and extending therefrom toward the inner peripheral wall 102 of the firing tube 100. In certain embodiments, the launch tube 110 forms a gap between the launch tube 110 and the inner peripheral wall 102 so that the launcher becomes too hot or the structural integrity of the launcher is compromised or broken. It is configured to provide a desired amount of gas leakage so as not to include a fresh gas. Thus, embodiments of launch tube 110 may be sized to limit gas leakage and / or limit acoustic propagation of sound waves that occur during the UAV 108 firing process.

  The inner peripheral wall 102 may be formed from a prepreg substrate, such as an epoxy prepreg Kevlar (trade name). The stop 124 may be a rigid member formed from a thermoplastic polymer such as polyvinyl chloride (PVC) or from a metal such as aluminum or steel. The stopper 124 is rotationally restricted with respect to the UAV 108 and the launch tube 110 by the inner peripheral wall 102 of the launch tube 100.

  FIG. 2 is an enlarged view of the expandable skirt 132, adhesive bond 138, and shell 136 initially shown in FIG. 1, with gas pressure being formed in the high pressure volume 114 relative to the expandable skirt 132. Yes. The expandable skirt 132 is removably connected to the shell 136 using an adhesive bond 138. In alternative embodiments, the adhesive bond 138 may include other coupling methods configured to break when the gas 200 reaches a predetermined gas pressure within the high pressure volume 114, such as an expandable skirt 132. An appropriate pin or the like connected to the shell 136 may be replaced. The circumferential skirt protrusion 140 abuts against the inner peripheral wall 102 when the gas 200 is introduced into the hollow of the launch tube.

  FIG. 3 is an enlarged view of the expandable skirt 132 and shell 136 initially shown in FIG. 1, in which the gas in the high pressure volume is broken to break the adhesive bond 138 that restrains the launch tube within the launch tube 100. The pressure is pushing the expandable skirt. When the predetermined pressure is reached, the adhesive bond 138 is insufficient to keep the expandable skirt 132 bonded to the shell 136, and adhesive constraints between the outer surface of the shell 136 and the expandable skirt 132 are reduced. When broken, releases the expandable skirt 132 and the launch tube in the axial direction. The gas 200 continues to push the expandable skirt 132 against the inner peripheral wall 102 of the launch tube and reinforces the gas seal to push the launcher up above the launch tube. Although the expandable skirt 132 is adhesively coupled to the shell 136 at the base 300 of the launch tube 100 and shell 136 in the figure, the expandable skirt 132 may be connected at a higher position on the shell 136. Also, although the adhesive bond 138 has a bead or oblong shape in the figure, the adhesive bond 138 can be expanded as the gas 200 reaches a predetermined gas pressure in the high pressure volume 114. In order to push the skirt 132 away from the shell 136, the expandable skirt 132 may take the form of a thin layer of adhesive that can be “teared” or peeled away from the adhesive bond 138.

  FIG. 4 illustrates the launch tube 100 shown in FIG. 1 after the expandable skirt 132 has been released from the shell 136 around the gas generator 134. Gas generator 134 continues to generate gas 200 to pressurize high pressure volume 114, creating a differential pressure between high pressure volume 114 and other portions of the launch tube relative to expandable skirt 132, and a circumferential skirt. The gas seal which exists between the protrusion part 140 and the inner peripheral wall 102 is strengthened. The launch tube 110 thus pushes the UAV 108 up through the opening 106 and above the launch tube 100. The tether 116 coupled to the launch tube 110 is continuously fed out so that the launch tube 110 can continue to rise above the launch tube 100. The UAV 108 may remain removably coupled to the launch tube 110 through a stop 124 that is rotationally constrained by the inner peripheral wall 102 so that the stop 124 is UAV and the launcher stop tabs (122, 126). ) Is prevented from leaving at least one of. In FIG. 4, an opening 106 having a constant cross section is shown. In an alternative embodiment, the opening has a cross-section that expands in stages to rotationally release the stop 124 from the UAV stop tab 122, from the launcher stop tab 126, or both. You may have.

  FIG. 5 illustrates one embodiment of a launch tube 500 having a constant cross-sectional area along its length, wherein the launch tube 510 is removably coupled to the UAV 512 using a stop 514, the stop 514 being The launch tube 510 and the UAV 512 are detachably connected to each other and are rotationally restricted by the inner peripheral wall 516 of the launch tube 500. In this example, a launch tube 500 is shown having an optional breakable seal 502 across the top opening of the launch tube 500. Two gas generating canisters (504, 506) are shown and located within the high pressure volume 508 of the launch tube 500. In FIG. 5, the adhesive bond that restrained the launch tube 510 within the launch tube 500 is broken (see FIG. 3), and the pressure difference between the high pressure volume 508 and the high pressure volume of the launch tube opposite the opposite side. In response, the launch tube 510 has moved axially above the launch tube. UAV 512 is shown beginning to break out of projectile 500 through breachable seal 502, and stop 514 is rotationally constrained by inner wall 516 to maintain a detachable connection between launch tube 510 and UAV 512. It continues to be.

  FIG. 6 illustrates the UAV launch tube of FIG. 5 with the gas generating canisters (504, 506) —as shown in gas 600 —within the high pressure volume 508 between the inner peripheral wall 516 of the launch tube 500 and the launch tube 510. The pressure is increasing. A tether 604 is attached to the inner peripheral wall 516 and / or the inner base wall 606 via a tether reel or take-up device 608. Compared to FIG. 5, the launch tube 510 moves along the launch tube 500 along with the UAV 512-in this example, the volume of the rectangular parallelepiped-and the UAV 512 is detachably connected to the launch tube 510 by a stopper 514. Yes. In one embodiment, gas generation by the gas generators (504, 506) may be staggered such that the pressure is increased or maintained as the UAV 512 is moved along the launch tube 500 and ejected. This gas generator may be started later than the other.

  FIG. 7 illustrates the launch tube of FIGS. 5 and 6, preventing the launch tube 510 from exiting the launch tube and substantially retaining the gas in the launcher volume to the subsequent ambient atmosphere. To control gas leakage, the launch tube 510 is approaching the maximum delivery or maximum travel distance limited by the tether 604. In some embodiments, a hot or warm gas generator is used, and the launch tube 510 does not move substantially beyond the position shown in FIG. As the stop 514 slides through the inner peripheral wall 516, the stop 514 is separated from the UAV stop tab 700, allowing the UAV 512 to continue out of the launch tube without interference. In some embodiments, the stop 514 can be moved away from the UAV stop tab 700 by extending the maximum travel distance of the launch tube 510, such as by allowing the stop 514 to be completely away from the inner wall 516. It may be separable from both the stopper tab 702 of the tube. In such an embodiment, the launcher 510, or an expandable launcher skirt 704 of a portion of the launcher 510, can effectively deliver gas into the launcher volume to control subsequent gas leakage to the surrounding atmosphere. Hold on. The launcher also has a side indentation (not shown) to provide control of the release of gas through the launcher 510 at the maximum extended position, regardless of whether the stop 514 is fully removed. ).

  FIG. 8 illustrates one embodiment of a launch tube 800 having an enlarged open launch end. The stop 514 is rotationally constrained by the inner peripheral wall 820 of the firing tube 800 along a portion of the length of the firing tube, rather than along the entire length as shown in FIGS. Two gas generating canisters (802, 804) are shown disposed within the high pressure volume 806 of the launch tube 800. The moored launch tube 808 is shown disposed between the gas generation canisters (802, 804) and the UAV 810. The launch tube has a high-pressure opening 812 of constant cross-sectional area to increase the firing speed and an enlarged opening launch 814 to accommodate a UAV mount 816 that extends outside the fuselage of a conventional UAV 810. For example, the UAV mount 816 is provided for a camera, sensor, or other device that extends outside the fuselage of the UAV 810. The UAV 810 is shown breaching any destructible seal 818 and starting to be ejected from the launcher 800, and the stop 514 maintains a removable connection between the launch tube 808 and the UAV 810. The rotation is continuously restricted by the inner peripheral wall 820.

  FIG. 9 illustrates the enlarged aperture launcher 814 and the UAV launch tube 800 of FIG. 8, where the gas generating canister (802, 804) is a high pressure volume 806 between the launch tube 808 and the gas generating canister (802, 804). Inside, as shown by gas 900, the pressure is increased. A tether 902 is attached to the inner peripheral wall 820 and / or the inner base wall 904 via a tether reel or winding device 906. Compared to FIG. 8, the launch tube 808 moves with the UAV 810 along the launch tube 800—in this example, the volume of the cuboid—and the UAV 810 is detachably connected to the launch tube 808 by a stop 514. . In the embodiment shown in FIGS. 8 and 9, the launch tube 808 is not yet close to the enlarged aperture launch portion 814, and the stop 514 is still rotationally constrained by the inner wall 820 so that the UAV 810 can be attached to and detached from the launch tube 808. It is linked to.

  FIG. 10 illustrates that the stop 514 shown in FIGS. 8 and 9 is disengaged from the UAV 810 and the UAV 810 separates from the launch tube 808 within the expanded aperture launch 814 of the launch tube. As the stop 514 slides past the high cross-sectional high pressure opening 812, the stop 514 is no longer rotationally constrained by the inner wall 820, the stop 514 is disengaged from the UAV stop tab 1000 and the UAV 810 is It is possible to continue out of the launch tube in an unconstrained state. In some embodiments, the launch tube 808 has an expandable launch tube skirt 1002 that substantially retains gas in the launcher volume and substantially through the enlarged aperture launch 814. Is configured to continue to promote.

  FIGS. 11 and 12 illustrate one embodiment of a launch tube 1100 having an enlarged aperture launch 1104. The launch tube 1100 has a high-pressure opening 1102 having a constant cross-sectional area for increasing the firing speed, and an enlarged opening launching part 1104 for accommodating a UAV mounting 1106 extending outside the fuselage of the UAV 1108. Unlike the launch tube shown in FIGS. 8 and 9, a high cross-sectional area high pressure opening 1102 extends substantially the entire length of the launch tube 1100. In the embodiment shown in FIGS. 11 and 12, the enlarged aperture launch end 1104 is the length of the launch tube to accommodate the UAV payload 1106 in the front of the UAV 1108 while maximizing the length of the available high pressure aperture. It has been introduced suddenly along. The stopper 1110 removably couples the UAV 1108 to the launch tube 1112 and is rotationally restrained by the inner peripheral wall 1114 of the launch tube 1100 along a substantial portion of the length of the launch tube before reaching the enlarged opening 1104. Thus, the stop 1110 does not rotate away from the UAV 1108 and the launch tube 1112. When the stop 1110 slides past the inner wall 1114 of the high pressure opening 1102, the stop 1110 is no longer rotationally constrained by the inner wall 1114, the stop 1110 is disengaged from the UAV 1108 and the UAV 1108 is not constrained. It will be possible to continue to go outside.

  FIG. 13 is a bottom perspective view of an exemplary UAV 1300 prior to launch, ie, the main wing 1302 and tail plane 1304 are folded under the fuselage of the aircraft. Also shown is a propeller hub 1306 to which the propeller can be rotatably mounted. The aircraft may include a radio frequency (RF) antenna that follows or extends from the shape of the aircraft. Whether the tube volume is a right cylinder, cuboid, or other shape, the UAV cross-section is insufficient to maintain an airtight adhesion between the aircraft and the inner wall of the launcher. For this reason, a launch tube is placed between the gas source and the UAV for launching based on gas pressure.

  FIG. 14 illustrates an exemplary UAV 1400 in a fired state with the wings 1302, 1304 deployed and the propeller prop 1402 rotating. The UAV may receive and / or transmit signals through the antenna, for example, the RF antenna 1308 may follow or extend from the shape of the fired UAV 1400.

Various combinations and / or sub-combinations of the specific features and forms of the above embodiments may be created, and these are still intended to be within the scope of this invention. Thus, it should be understood that various features and forms of the disclosed embodiments may be combined with or substituted for each other to form various modes of the disclosed invention. Furthermore, the scope of the invention disclosed herein by way of example should not be limited to the specific embodiments disclosed above.

Claims (34)

In unmanned aerial vehicle (UAV) launch tube equipment:
At least one layer of prepreg substrate provided around the opening and forming a tube;
A launcher disposed within the tube and having a first stop tab;
A stop detachably connected to the first stop tab and in contact with an inner peripheral wall of the tube;
The UAV launch tube apparatus, wherein the stopper is rotationally restrained by the inner peripheral wall and the first stopper tab.   The apparatus of claim 1, wherein the firing tube further comprises an expandable skirt that provides a pressure seal with the inner peripheral wall of the tube.   The apparatus of claim 1, wherein the expandable skirt is axially constrained within the tube by an adhesive.   4. The apparatus of claim 3, wherein the adhesive removably couples the expandable skirt around a shell in the tube. The apparatus of claim 4, wherein the shell is:
Including an outer surface of a gas generator, the gas generator configured to generate gas between the expandable skirt and the shell;
The generated pressure of the generated gas is sufficient to push the expandable skirt away from the shell by breaking the adhesive restraint between the outer surface of the shell and the expandable skirt. A device characterized by that.   5. The apparatus of claim 4, further comprising a UAV installed on the launch tube, the UAV having a second stop tab removably coupled to the stop, wherein the stop is An apparatus characterized in that it is rotationally constrained by the inner peripheral wall, the first stopper tab, and the second stopper tab.   5. A device according to claim 4, wherein the launch tube is moored to the tube. The apparatus of claim 1, wherein the launch tube is:
A base firing tube configured to engage the UAV and having a first plurality of partially expandable skirt seals;
A circumferential launcher skirt installed on the base launcher and having a second plurality of partially expandable skirt seals;
The apparatus wherein the first and second plurality of partially expandable skirt seals complete the inner wall pressure seal.   9. The apparatus of claim 8, wherein the expandable skirt is axially constrained within the tube by an adhesive.   10. The apparatus of claim 9, wherein the adhesive removably couples the expandable skirt around a shell in the tube, and the generation of gas by a gas generator inside the shell A device that pushes the expandable skirt away from the shell by breaking a detachable bond. 10. The apparatus of claim 9, further comprising a UAV installed on the launch tube, the UAV having a second stop tab removably coupled to the stop;
The apparatus wherein the inner peripheral wall prevents the stop from coming off the second stop tab while the UAV is in the tube. An unmanned aerial vehicle (UAV) launch method includes:
Generating gas in the gas generator;
Introducing the generated gas into a high pressure volume between the expandable launcher skirt of the launcher and the gas generator to break the adhesive bond that restrains the launcher in the launcher;
Using the generated gas to push the expandable launcher skirt against the inner peripheral wall of the launcher;
A method of launching a UAV comprising the step of using the generated gas to push up the launch tube above the launch tube.   13. The method of claim 12, wherein the adhesive bond includes an adhesive bond between the expandable skirt and a shell around the gas generator. The method of claim 12, further comprising:
Fastening the UAV to the cannon using a stop;
Restraining the stop against the inner peripheral wall of the launch tube to prevent the stop from detaching from at least one of the UAV and the launch tube;
A method characterized by comprising. 15. The method of claim 14, further comprising:
Sliding the stop through the inner peripheral wall to release the stop from at least one of the UAV and the launch tube. 15. The method of claim 14, further comprising:
A method comprising mooring the launch tube to the launch tube to prevent the launch tube from exiting the launch tube. An unmanned aerial vehicle (UAV) launch method includes:
Constraining the launch tube within the launch tube;
Introducing gas into the high pressure side of the expandable launcher skirt of the launcher to break the restraint of the launcher in the launcher;
Using the gas to push the launch tube up above the launch tube;
A method for launching a UAV, comprising: The method of claim 17, further comprising:
Using the gas to push the expandable launcher skirt against the inner wall of the launch tube.   19. The method of claim 18, wherein the step of constraining the firing tube comprises the step of restraining the firing tube using an adhesive.   20. The method of claim 19, wherein constraining the firing tube with the adhesive further comprises constraining the expandable skirt of the firing tube to a shell around a gas generator in the firing tube. A method characterized by. 21. The method of claim 20, further comprising:
A method comprising mooring the launch tube to the launch tube.   18. The method of claim 17, wherein the expandable launcher skirt further comprises a circumferential skirt projection extending from the expandable launcher skirt toward the inner peripheral wall of the launcher tube. The method of claim 17, further comprising:
Limiting the movement of the launch tube by a tether configured to prevent the launch tube from exiting the launch tube, wherein limiting the movement of the launch tube substantially causes the gas to enter the launch tube. The method characterized by hold | maintaining.   24. The method of claim 23, wherein the tether is attached to an inner peripheral wall of the firing tube and the firing tube by at least one of a tether reel and a winding device. In unmanned aerial vehicle (UAV) launch tube devices:
A first opening having a constant cross-sectional area;
A second opening having an enlarged cross-sectional area compared to the first opening, wherein the first opening and the second opening form a launch tube;
A launch tube disposed in the first opening and configured to be removably coupled to the UAV; and
The UAV launch tube apparatus, wherein the launch tube is configured to be detached from the UAV when the launch tube moves from the first opening to the second opening.   26. The apparatus of claim 25, wherein the launch tube is configured to be detachably coupled to the UAV by a stop, the stop being a first stop tab of the launch tube, and a first of the UAV. 2. An apparatus configured to be removably coupled to a two stop tab.   27. The apparatus of claim 26, wherein the stop is rotated by at least one of: an inner surface of the first opening, a first stop tab of the launch tube, and a second stop tab of the UAV. A device characterized by being constrained.   28. The apparatus of claim 27, wherein the stop is configured to detach from the second stop tab of the UAV when the launcher moves from the first opening to the second opening. A device characterized by comprising.   29. The apparatus of claim 28, wherein the stop is configured to disengage from the first stop tab of the launch tube when the stop moves through the inner surface of the second opening. A device characterized by. 26. The apparatus of claim 25, further:
At least one gas generator disposed at the bottom of the first opening;
An expandable launcher skirt of the launcher, the open end of the expandable launcher skirt being directed to the at least one gas generator and axially restrained by a detachable restraint Tube skirt;
A device characterized by comprising.   32. The apparatus of claim 30, wherein the at least one gas generator is configured to generate gas, and the expandable launcher skirt is configured to substantially retain the gas within the launch tube. A device characterized by that.   32. The apparatus of claim 31, wherein the generated gas causes the expandable launcher skirt to disengage from the removable restraint and propel the launcher from the first opening to the second opening. A device characterized in that it is configured.   34. The apparatus of claim 32, wherein the expandable launcher skirt expands to an enlarged cross-sectional area of the second opening to substantially retain the gas within the second opening of the launch tube. A device characterized in that it is configured to continue. 33. The apparatus of claim 32, further comprising: a tether attached to the launch tube and a bottom of the first opening, the tether configured to limit movement of the launch tube, and the expansion A possible skirt holds the gas substantially free from leaking through the opening of the launch tube.

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